Siemens Aktiengesellschaft

Manjit Shivanand

Ching-Pang Lee

Kok-Mun Tham

Gm Salam Azad

Vincent Paul Laurello

Nicholas F Martin, Jr

Eric Joseph Schroeder

Abdullatif M Chehab

Christopher K Rawlings

Erik Johnson

Shantanu P Mhetras

Ralph W Matthews

Dustin Jaime Muller

Steven Coppess

Kahwai G Muriithi

A seal assembly between a hot gas path and a disc cavity in a turbine engine includes a non-rotatable vane assembly including a row of vanes and an inner shroud, a rotatable blade assembly axially adjacent to the vane assembly and including a row of blades and a turbine disc that forms a part of a turbine rotor, and an annular wing member located radially between the hot gas path and the disc cavity. The wing member extends generally axially from the blade assembly toward the vane assembly and includes a plurality of circumferentially spaced apart flow passages extending therethrough from a radially inner surface thereof to a radially outer surface thereof. The flow passages each include a portion that is curved as the passage extends radially outwardly to effect a scooping of cooling fluid from the disc cavity into the flow passages and toward the hot gas path.

Outer rim seal assembly in a turbine engine

A seal assembly between a disc cavity and a hot gas path in a gas turbine engine includes a stationary vane assembly and a rotating blade assembly axially upstream from the vane assembly. A platform of the blade assembly has a radially outwardly facing first surface, an axially downstream facing second surface defining an aft plane, and a plurality of grooves extending into the second surface such that the grooves are recessed from the aft plane The grooves are arranged such that a circumferential space is defined between adjacent grooves During operation of the engine, the grooves impart a circumferential velocity component to purge air flowing out of a disc cavity through the grooves to guide the purge air toward a hot gas path such that the purge air flows in a desired direction with reference to a direction of hot gas flow through the hot gas path.

Seal assembly including grooves in an aft facing side of a platform in a gas turbine engine

A gas turbine having rotor discs (), a disc cavity () and a stator stage () extending to the disc cavity (). Seal housing flanges () extend from a seal housing () of the stator stage (). Rotor flanges () extend from a rotor disk (-). An inner rotor flange () and first seal housing flange () are inward from a second seal housing flange (). One rotor flange () is outward from the second seal housing flange (). The inner rotor flange () and first seal housing flange () extend toward one another to limit movement of main gas flow (). An inlet () injects air () between the outward rotor flange () and second seal housing flange ().

Flow discourager integrated turbine inter-stage U-ring

An airfoil in a gas turbine engine includes an outer wall, a cooling fluid cavity, and a cooling system. The outer wall has a leading edge, a trailing edge, a pressure side, a suction side, and radially inner and outer ends. The cooling fluid cavity is defined in the outer wall, extends generally radially between the inner and outer ends of the outer wall, and receives cooling fluid for cooling the outer wall. The cooling system receives cooling fluid from the cooling fluid cavity for cooling the trailing edge portion of the outer wall and includes a cooling fluid chamber defined by opposing first and second sidewalls that include respective alternating angled sections that provide the cooling fluid chamber with a zigzag shape.

Cooling system including wavy cooling chamber in a trailing edge portion of an airfoil assembly

A seal assembly between a hot gas path and a disc cavity in a turbine engine includes a non-rotatable vane assembly including a row of vanes and an inner shroud, a rotatable blade assembly adjacent to the vane assembly and including a row of blades and a turbine disc that forms a part of a turbine rotor, and an annular wing member located radially between the hot gas path and the disc cavity. The wing member extends generally axially from the blade assembly toward the vane assembly and includes a plurality of circumferentially spaced apart flow passages extending therethrough from a radially inner surface thereof to a radially outer surface thereof. The flow passages effect a pumping of cooling fluid from the disc cavity toward the hot gas path during operation of the engine.

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Winter Springs, FL, United States of America

Manjit Shivanand